EP2971646A1 - Système de gestion thermique de turbine à gaz - Google Patents

Système de gestion thermique de turbine à gaz

Info

Publication number
EP2971646A1
EP2971646A1 EP14779541.3A EP14779541A EP2971646A1 EP 2971646 A1 EP2971646 A1 EP 2971646A1 EP 14779541 A EP14779541 A EP 14779541A EP 2971646 A1 EP2971646 A1 EP 2971646A1
Authority
EP
European Patent Office
Prior art keywords
fluid
heat exchanger
recited
characteristic
gas turbine
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP14779541.3A
Other languages
German (de)
English (en)
Other versions
EP2971646B1 (fr
EP2971646A4 (fr
Inventor
Federico Papa
Thomas G. Phillips
Kathleen R. Phillips
Ethan K. Stearns
Justin W. Heiss
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
RTX Corp
Original Assignee
United Technologies Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from US13/799,406 external-priority patent/US9334802B2/en
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of EP2971646A1 publication Critical patent/EP2971646A1/fr
Publication of EP2971646A4 publication Critical patent/EP2971646A4/fr
Application granted granted Critical
Publication of EP2971646B1 publication Critical patent/EP2971646B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • F02C7/224—Heating fuel before feeding to the burner
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/213—Heat transfer, e.g. cooling by the provision of a heat exchanger within the cooling circuit
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/303—Temperature
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/306—Mass flow
    • F05D2270/3062—Mass flow of the auxiliary fluid for heating or cooling purposes

Definitions

  • This disclosure relates generally to a gas turbine engine, and more particularly to a gas turbine engine thermal management system that manages the heat generated by a gas turbine engine.
  • Gas turbine engines such as turbofan gas turbine engines, generally include a fan section, a compressor section, a combustor section and a turbine section.
  • airflow is pressurized in the compressor section and is mixed with fuel and burned in the combustor section.
  • the hot combustion gases that are generated in the combustor section are communicated through the turbine section.
  • the turbine section extracts energy from the hot combustion gases to power the compressor section, the fan section and other gas turbine engine loads.
  • a thermal management system can be employed within the gas turbine engine to manage the heat generated by the gas turbine engine.
  • Thermal management systems maintain operable temperatures for the engine fuel, oil and other fluids that are communicated throughout the engine. For example, a portion of the heat of the engine oil can be transferred into the engine fuel to increase the efficiency of the gas turbine engine.
  • a thermal management system for a gas turbine engine includes, among other things, a heat exchanger and a valve that controls an amount of a first fluid that is communicated through the heat exchanger
  • a first sensor senses a first characteristic of a second fluid that is communicated through the heat exchanger to exchange heat with the first fluid and a second sensor senses a second characteristic of the second fluid.
  • a positioning of the valve is based on at least one of the first characteristic and the second characteristic.
  • a controller is operable to receive a signal from each of the first sensor and the second sensor.
  • the controller modulates the valve to communicate the amount of the first fluid to the heat exchanger in response to at least one of the signal from the first sensor and the signal from the second sensor.
  • the first characteristic includes temperature information and the second characteristic includes pressure information.
  • the controller modulates the valve to communicate the amount of the first fluid to the heat exchanger in response to at least one of: altitude information, ambient temperature information, or engine power condition information.
  • the first sensor senses a temperature of the second fluid after the second fluid exits the heat exchanger.
  • the system comprises a pump, and the second sensor senses a flow rate of the second fluid through the pump.
  • the first fluid is oil and the second fluid is fuel.
  • the heat exchanger is part of a first fluid circuit that also includes a second heat exchanger and a third heat exchanger.
  • the heat exchanger is incorporated into a second fluid circuit in addition to the first fluid circuit.
  • a gas turbine engine includes, among other things, a thermal management system that includes a first fluid circuit and a second fluid circuit that manage heat generated in at least a portion of the gas turbine engine.
  • a first heat exchanger is incorporated into each of the first fluid circuit and the second fluid circuit and a second heat exchanger is incorporated into the first fluid circuit.
  • a valve controls an amount of a first fluid that is communicated to the first heat exchanger and the second heat exchanger.
  • a controller is configured to control a positioning of the valve. The amount of the first fluid communicated to the first heat exchanger is based on a first characteristic of a second fluid and the amount of the first fluid communicated to the second heat exchanger is based on a second characteristic of the second fluid.
  • the first fluid circuit circulates oil.
  • the second fluid circuit circulates fuel.
  • a first sensor senses the first characteristic and a second sensor senses the second characteristic.
  • the first fluid circuit incorporates a third heat exchanger.
  • the first fluid circuit communicates a conditioned first fluid to at least one engine system and the second fluid circuit communicates a conditioned second fluid to at least a combustor section of the gas turbine engine.
  • a method of controlling a thermal management system of a gas turbine engine includes, among other things, sensing a first characteristic of a first fluid, sensing a second characteristic of the first fluid, and controlling an amount of a second fluid that is communicated through a circuit of the thermal management system based on at least one of the first characteristic and the second characteristic.
  • the step of controlling includes closing a valve of the thermal management system to prevent the flow of the second fluid to a heat exchanger of the circuit during engine idle conditions.
  • the step of controlling includes modulating a valve of the thermal management system to an intermediate position to communicate at least a portion of the second fluid to a heat exchanger of the circuit during engine cruise conditions.
  • the step of controlling includes modulating a valve of the thermal management system to a fully open position to communicate the second fluid to a heat exchanger of the circuit during engine takeoff conditions.
  • Figure 1 schematically illustrates a gas turbine engine.
  • Figure 2 illustrates an exemplary thermal management system for a gas turbine engine.
  • FIG. 1 schematically illustrates a gas turbine engine 20.
  • the exemplary gas turbine engine 20 is a two-spool turbofan engine that generally incorporates a fan section 22, a compressor section 24, a combustor section 26 and a turbine section 28.
  • Alternative engines might include an augmenter section (not shown) among other systems for features.
  • the fan section 22 drives air along a bypass flow path B, while the compressor section 24 drives air along a core flow path C for compression and communication into the combustor section 26.
  • the hot combustion gases generated in the combustor section 26 are expanded through the turbine section 28.
  • FIG. 1 schematically illustrates a gas turbine engine 20.
  • the exemplary gas turbine engine 20 is a two-spool turbofan engine that generally incorporates a fan section 22, a compressor section 24, a combustor section 26 and a turbine section 28.
  • Alternative engines might include an augmenter section (not shown) among other systems for features.
  • the fan section 22 drives air along a bypass flow path B, while the compressor section 24 drives
  • the gas turbine engine 20 generally includes a low speed spool 30 and a high speed spool 32 mounted for rotation about an engine centerline longitudinal axis A.
  • the low speed spool 30 and the high speed spool 32 may be mounted relative to an engine static structure 33 via several bearing systems 31. It should be understood that other bearing systems 31 may alternatively or additionally be provided.
  • the low speed spool 30 generally includes an inner shaft 34 that interconnects a fan 36, a low pressure compressor 38 and a low pressure turbine 39.
  • the inner shaft 34 can be connected to the fan 36 through a geared architecture 45 to drive the fan 36 at a lower speed than the low speed spool 30.
  • the high speed spool 32 includes an outer shaft 35 that interconnects a high pressure compressor 37 and a high pressure turbine 40.
  • the inner shaft 34 and the outer shaft 35 are supported at various axial locations by bearing systems 31 positioned within the engine static structure 33.
  • a combustor 42 is arranged between the high pressure compressor 37 and the high pressure turbine 40.
  • a mid-turbine frame 44 may be arranged generally between the high pressure turbine 40 and the low pressure turbine 39.
  • the mid- turbine frame 44 can support one or more bearing systems 31 of the turbine section 28.
  • the mid-turbine frame 44 may include one or more airfoils 46 that extend within the core flow path C.
  • the inner shaft 34 and the outer shaft 35 are concentric and rotate via the bearing systems 31 about the engine centerline longitudinal axis A, which is co- linear with their longitudinal axes.
  • the core airflow is compressed by the low pressure compressor 38 and the high pressure compressor 37, is mixed with fuel and burned in the combustor 42, and is then expanded over the high pressure turbine 40 and the low pressure turbine 39.
  • the high pressure turbine 40 and the low pressure turbine 39 rotationally drive the respective high speed spool 32 and the low speed spool 30 in response to the expansion.
  • the pressure ratio of the low pressure turbine 39 can be pressure measured prior to the inlet of the low pressure turbine 39 as related to the pressure at the outlet of the low pressure turbine 39 and prior to an exhaust nozzle of the gas turbine engine 20.
  • the bypass ratio of the gas turbine engine 20 is greater than about ten (10:1)
  • the fan diameter is significantly larger than that of the low pressure compressor 38
  • the low pressure turbine 39 has a pressure ratio that is greater than about five (5:1). It should be understood, however, that the above parameters are only exemplary of one embodiment of a geared architecture engine and that the present disclosure is applicable to other gas turbine engines, including direct drive turbofans.
  • TSFC Thrust Specific Fuel Consumption
  • Fan Pressure Ratio is the pressure ratio across a blade of the fan section 22 without the use of a Fan Exit Guide Vane system.
  • the low Fan Pressure Ratio according to one non-limiting embodiment of the example gas turbine engine 20 is less than 1.45.
  • Low Corrected Fan Tip Speed is the actual fan tip speed divided by an industry standard temperature correction of [(Tram °R) / (518.7 °R)] 0'5 .
  • the Low Corrected Fan Tip Speed according to one non-limiting embodiment of the example gas turbine engine 20 is less than about 1150 fps (351 m/s).
  • Each of the compressor section 24 and the turbine section 28 may include alternating rows of rotor assemblies and vane assemblies (shown schematically) that carry airfoils that extend into the core flow path C.
  • the rotor assemblies can carry a plurality of rotating blades 25, while each vane assembly can carry a plurality of vanes 27 that extend into the core flow path C.
  • the blades 25 create or extract energy (in the form of pressure) from the core airflow that is communicated through the gas turbine engine 20 along the core flow path C.
  • the vanes 27 direct the core airflow to the blades 25 to either add or extract energy.
  • gas turbine engine 20 generate heat during engine operation, including the fan section 22, the compressor section 24, the combustor section 26 and the turbine section 28. This heat may be carried by fluids that are communicated throughout these and other various sections of the gas turbine engine 20.
  • engine fuel and engine oil are circulated throughout the gas turbine engine 20 and carry a portion of the heat that is generated during engine operation.
  • fluid is intended to include fuel, oil, lubricating fluids, hydraulic fluids or any other fluids circulated through the gas turbine engine 20.
  • FIG 2 illustrates a thermal management system 100 for a gas turbine engine, such as the gas turbine engine 20 illustrated by Figure 1.
  • the thermal management system 100 can manage the heat generated by the gas turbine engine 20 during its operation.
  • the thermal management system 100 can communicate conditioned fluids to various engine systems of the gas turbine engine 20 to minimize this heat generation and dissipate the heat.
  • the thermal management system 100 can simultaneously deliver conditioned fluids having different temperatures to both low temperature systems and high temperature systems of the gas turbine engine 20, as is further discussed below.
  • the term "conditioned fluid" is intended to include heated, cooled and/or pressurized fluids. Of course, this view is highly schematic and is not necessarily shown to the scale it would be in practice.
  • the thermal management system 100 is mounted to the gas turbine engine 20.
  • the mounting location of the thermal management system 100 is application specific.
  • Non-limiting example mounting locations for the thermal management system 100 include the engine static structure 33 (see Figure 1), a core compartment, a fan compartment, a bypass fan passage and other locations.
  • the thermal management system 100 includes a first fluid circuit 60 and a second fluid circuit 62.
  • the first fluid circuit 60 can circulate a first fluid 81, such as engine oil
  • the second fluid circuit 62 can circulate a second fluid 87, such as engine fuel.
  • first fluid circuit 60 and the second fluid circuit 62 transfer heat between the fluids communicated through the separate circuits 60, 62 to manage the temperatures of these fluids, as is further discussed below.
  • the first fluid circuit 60 incorporates a fluid tank 64, a first heat exchanger 66, a second heat exchanger 68, a third heat exchanger 70 and a pump 72.
  • the pump 72 pumps a first fluid (indicated by arrow 81), such as oil, from the fluid tank 64 along a passage 74 to an inlet 76 of the first heat exchanger 66.
  • the first fluid circuit 60 can include a filter 78 for filtering the first fluid 81 prior to communicating the first fluid 81 to the inlet 76.
  • the first fluid circuit 60 can include a trim passage 80 for returning a portion of the first fluid 81 to the fluid tank 64 in the event an excess amount of the first fluid 81 is pumped from the fluid tank 64.
  • the first fluid 81 is communicated through the first heat exchanger 66 and exchanges heat with a different, third fluid 82, such as air, to condition the first fluid 81.
  • the first heat exchanger 66 is an air/oil cooler that exchanges heat between oil and air.
  • Heat from the first fluid 81 is transferred into the third fluid 82 to provide a first conditioned fluid 83 that exits an outlet 84 of the first heat exchanger 66.
  • the first conditioned fluid 83 is communicated along a passage 86 to a valve 88.
  • the valve 88 controls the amount of the first conditioned fluid 83 that is communicated to the second heat exchanger 68 and the third heat exchanger 70.
  • the second heat exchanger 68 either receives an entirety of the first conditioned fluid 83 that is received by the valve 88, or receives only a portion thereof, as is further detailed below.
  • the first and second heat exchangers 66, 68 are in continuous operation during operation of the thermal management system 100, but the third heat exchanger 70 is only selectively operated as required.
  • a first portion 85 of the first conditioned fluid 83 is communicated to an inlet 92 of the second heat exchanger 68 along a passage 90.
  • the first portion 85 of the first conditioned fluid 83 is communicated through the second heat exchanger 68 and exchanges heat with the second fluid 87, such as fuel, that is circulated through the second fluid circuit 62.
  • the second heat exchanger 68 renders a second conditioned fluid 89 which is communicated through an outlet 94 of the second heat exchanger 68 and into a passage 96.
  • a second portion 91 of the first conditioned fluid 83 can be communicated along a passage 98 to an inlet 102 of the third heat exchanger 70.
  • the second portion 91 of the first conditioned fluid 83 is communicated through the third heat exchanger 70 and exchanges heat with yet another fluid 104, such as air, to render a third conditioned fluid 93 that exits the third heat exchanger 70 at outlet 106.
  • the third conditioned fluid 93 from the third heat exchanger 70 is communicated along a passage 108 and is eventually communicated into the passage 96 such that the second conditioned fluid 89 from the second heat exchanger 68 and the third conditioned fluid 93 from the third heat exchanger 70 are mixed together to render a mixed conditioned fluid 95.
  • a first portion 97 of the mixed conditioned fluid 95 is communicated to a first engine system 110 along a passage 112.
  • a second portion 99 of the mixed conditioned fluid 95 is communicated along passage 114 and is mixed with a third portion 101 of the first conditioned fluid 83 (communicated from the first heat exchanger 66 along a bypass passage 116 that extends between the first heat exchanger 66 and a second engine system 118) and is communicated to a second engine system 118.
  • conditioned fluids having varying temperatures can be delivered to separate engine systems.
  • a mixture of the second portion 99 of the mixed conditioned fluid 95 and the third portion 101 of the first conditioned fluid 83 can include a greater temperature than the first portion 97 of the mixed conditioned fluid 95.
  • the first engine system 110 could include a portion of the geared architecture 48 of the fan section 22, such as journal bearings or other parts of the geared architecture 48.
  • the second engine system 118 could include an engine bearing compartment, an engine gearbox or a drive mechanism of the geared architecture 48. Although only two engine systems are illustrated, it should be understood that additional or fewer engine systems can receive conditioned fluids from the thermal management system 100.
  • the second fluid circuit 62 of the thermal management system 100 includes a fluid tank 120, the second heat exchanger 68 (which is also incorporated into the first fluid circuit 60) and a pump 122.
  • the second fluid circuit 62 can also optionally include a secondary pump 136.
  • the fluid tank 120 stores the second fluid 87 that is different from the first fluid 81 for use by the gas turbine engine 20.
  • the second fluid 87 is fuel.
  • the pump 122 pumps the second fluid 87 from the fluid tank 120 along a passage 124 and through the second heat exchanger 68 along a passage 126 to extract heat from the first portion 85 of the first conditioned fluid 83 that is communicated through the second heat exchanger 68 in the first fluid circuit 60.
  • a conditioned second fluid 105 is delivered along a passage 128 to a portion of the gas turbine engine, such as the combustor section 26 for generating the hot combustion gases that flow to the turbine section 28.
  • a portion 107 of the conditioned second fluid 105 can be returned to the passage 124 via a bypass passage 130.
  • the second fluid circuit 62 can also incorporate a sensor 132 (i.e., a first sensor), such as a temperature sensor or other suitable sensor.
  • the sensor 132 monitors the temperature of the conditioned second fluid 105.
  • the sensor 132 communicates with an engine controller 134.
  • the engine controller 134 is programed with the necessary logic to interpret the information from the sensor 132, among other information, and modulate a positioning of the valve 88.
  • the position of the valve 88 establishes what amount, if any, of the first conditioned fluid 83 will be communicated to the second and third heat exchangers 68, 70. In other words, the position of the valve 88 controls the amount of heat added to the second fluid 87 at different engine power conditions.
  • Other valves, sensors and controls examples of which are described below, could also be incorporated into the thermal management system 100.
  • the third heat exchanger 70 receives a portion of the first conditioned fluid 83 only if a temperature of the conditioned second fluid 105 of the second fluid circuit 62 is above a predefined threshold.
  • the predefined threshold is approximately 300° F/148.9 ° C, although the actual setting will depend on design specific parameters. If the sensor 132 alerts the engine controller 134 (via a signal, for example) that this predefined threshold has been exceeded, the engine controller 134 modulates the valve 88 to split a flow of the first conditioned fluid 83 between the second heat exchanger 68 and the third heat exchanger 70.
  • the second fluid circuit 62 of the thermal management system 100 can incorporate an additional sensor 140 (i.e., a second sensor) that is configured to sense a different characteristic from the sensor 132.
  • the sensor 140 is a fluid flow sensor that senses the flow rate, which may be based on pressure differentials, of the conditioned second fluid 105 that passes through the pump 122.
  • the sensor 140 monitors the flow rate of the conditioned second fluid 105 and can communicate flow rate information (i.e., pressure information) to the engine controller 134 for controlling a positioning of the valve 88.
  • the engine controller 134 may be programed with the necessary logic to interpret the information from the sensor 140 and modulate a positioning of the valve 88.
  • a positioning of the valve 88 can be controlled based on the flow rate information sensed by the sensor 140 to control what amount, if any, of the first conditioned fluid 83 will be communicated to the second and/or third heat exchangers 68, 70.
  • the amount of the first conditioned fluid 83 communicated to the second heat exchanger 68 is based on the flow rate information sensed by the sensor 140 (i.e., a first characteristic of the conditioned second fluid 105) and the amount of the first conditioned fluid 83 communicated to the third heat exchanger 70 is based on the temperature information sensed by the sensor 132 (i.e., a second characteristic of the conditioned second fluid 105).
  • the thermal management system 100 can be controlled similar to the following schedule.
  • the engine controller 134 may close the valve 88 to prevent the flow of the first conditioned fluid 83 to the second and/or third heat exchangers 68, 70.
  • the valve 88 may be modulated to an intermediate position (in response to a command from the engine controller 134) to communicate at least a portion of the first conditioned fluid 83 to the second and/or third heat exchangers 68, 70.
  • valve 88 may be modulated to a fully open position to communicate an increased amount of the first conditioned fluid 83 through the first and/or second heat exchangers 68, 70.
  • the schedule for controlling the positioning of the valve 88 is not intended to be limited to one that is a function of fluid temperature and/or pressure. Rather, the schedule for controlling the positioning of the valve 88 may be a function of other characteristics, including but not limited to, altitude information, ambient temperature information, and engine power condition information.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)

Abstract

La présente invention, selon un aspect donné à titre d'exemple, concerne un système de gestion thermique pour une turbine à gaz comprenant, entre autres, un échangeur de chaleur et un clapet qui commande une quantité d'un premier fluide qui est communiqué au travers de l'échangeur de chaleur. Un premier capteur détecte une première caractéristique d'un deuxième fluide qui est communiqué au travers de l'échangeur de chaleur à des fins d'échange avec le premier fluide et un deuxième capteur détecte une deuxième caractéristique du deuxième fluide. Un positionnement du clapet est basé sur au moins l'une parmi la première caractéristique et la deuxième caractéristique.
EP14779541.3A 2013-03-13 2014-03-10 Système de gestion thermique de turbine à gaz Active EP2971646B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/799,406 US9334802B2 (en) 2011-10-31 2013-03-13 Gas turbine engine thermal management system
PCT/US2014/022288 WO2014164397A1 (fr) 2013-03-13 2014-03-10 Système de gestion thermique de turbine à gaz

Publications (3)

Publication Number Publication Date
EP2971646A1 true EP2971646A1 (fr) 2016-01-20
EP2971646A4 EP2971646A4 (fr) 2016-11-16
EP2971646B1 EP2971646B1 (fr) 2020-12-16

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP14779541.3A Active EP2971646B1 (fr) 2013-03-13 2014-03-10 Système de gestion thermique de turbine à gaz

Country Status (2)

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EP (1) EP2971646B1 (fr)
WO (1) WO2014164397A1 (fr)

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6810674B2 (en) * 2002-07-18 2004-11-02 Argo-Tech Corporation Fuel delivery system
US8776952B2 (en) * 2006-05-11 2014-07-15 United Technologies Corporation Thermal management system for turbofan engines
US20090313999A1 (en) * 2008-05-13 2009-12-24 Scott Hunter Method and apparatus for controlling fuel in a gas turbine engine
US7984606B2 (en) * 2008-11-03 2011-07-26 Propulsion, Gas Turbine, And Energy Evaluations, Llc Systems and methods for thermal management in a gas turbine powerplant
US20100242492A1 (en) * 2009-03-30 2010-09-30 Honeywell International Inc. Distributed engine control systems and gas turbine engines
US20100313591A1 (en) * 2009-06-12 2010-12-16 Hamilton Sundstrand Corporation Adaptive heat sink for aircraft environmental control system
US8261527B1 (en) * 2012-01-31 2012-09-11 United Technologies Corporation Gas turbine engine with geared turbofan and oil thermal management system with unique heat exchanger structure

Also Published As

Publication number Publication date
WO2014164397A1 (fr) 2014-10-09
EP2971646B1 (fr) 2020-12-16
EP2971646A4 (fr) 2016-11-16

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